A pressure bulkhead (1) for an aircraft fuselage is depicted and described, having a skin element (3), which has a first surface (7) and a second surface (9), as well as a circumferential edge (11) and a center axis (13), and having a reinforcement assembly (5), which has a plurality of radially disposed reinforcement elements (15), which extend along the first surface (7) in a radial direction between an outer end (17) at the edge (11) of the skin element (3) and an inner end (19), which faces the center axis (13), wherein, as viewed in a cross section, which extends radially along the center axis (13), each of the radially disposed reinforcement elements (15) defines a first contour line (23) and defines a second contour line (25), which is located opposite said first contour line, wherein each contour line (23, 25) extends from the outer end (17, 19) of the radially disposed reinforcement elements (15) to the inner end thereof, and wherein the reinforcement assembly (5) rests with the first contour lines (23) thereof on the first surface (7) of the skin element (3). The object of the invention, which is to provide a pressure bulkhead for an aircraft fuselage that can absorb the occurring pressure loads in as efficient a manner as possible, is achieved in that each of the first and/or second contour lines (23, 25) has a convex course from the outer end (17) in a direction towards the inner end (19), in which the distance between the first contour line (23) and the second contour line (25) increases tangent continuously.
PRESSURE BULKHEAD FOR AN AIRCRAFT FUSELAGE
CLOISON ETANCHE POUR UN FUSELAGE D'AERONEF
2015-12-03
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |